Vehicle Heat Exchanger System

ABSTRACT

A vehicle is provided including a structure including a skin defining an outside surface exposed to ambient cooling flow and an inside surface. The structure includes a first structural member extending from the inside surface of the skin and a second structural member extending from the inside surface of the skin; and a thermal management system including a heat exchanger assembly positioned adjacent to, and in thermal communication with, the inside surface of the skin, the heat exchanger assembly positioned at least partially between the first and second structural members of the structure.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a non-provisional application claiming the benefitof priority under 35 U.S.C. § 119(e) to U.S. Provisional Application No.62/879,771, filed Jul. 29, 2019, which is hereby incorporated byreference in its entirety.

FIELD

The present subject matter relates generally to a thermal managementsystem for a vehicle utilizing an ambient airflow over a skin of thevehicle as a heat sink.

BACKGROUND

At least certain vehicles generate a relatively large amount of heatduring operation. For example, at least certain aircraft generate arelatively large amount of heat during operation of its thrustgenerating systems, such as during operation of one or more gas turbineengines, electric motors and generators, etc., as well as through otherflight-enabling accessory systems, such as hydraulic systems, electronicsystems, etc.

In order to reject a desired amount of such heat, certain aircraftinclude ram air coolers, externally mounted coolers, etc. However, suchcoolers may create additional drag on the aircraft, such as anadditional amount of parasitic drag. Accordingly, an aircraft or othervehicle including a thermal management system having one or morefeatures for rejecting heat without increasing a drag on the vehiclewould be useful.

BRIEF DESCRIPTION

Aspects and advantages of the invention will be set forth in part in thefollowing description, or may be obvious from the description, or may belearned through practice of the invention.

In one exemplary aspect of the present disclosure, a vehicle is providedincluding a structure including a skin defining an outside surfaceexposed to ambient cooling flow and an inside surface. The structureincludes a first structural member extending from the inside surface ofthe skin and a second structural member extending from the insidesurface of the skin; and a thermal management system including a heatexchanger assembly positioned adjacent to, and in thermal communicationwith, the inside surface of the skin, the heat exchanger assemblypositioned at least partially between the first and second structuralmembers of the structure.

In another exemplary embodiment of the present disclosure a thermalmanagement system for a vehicle is provided. The vehicle includes astructure having a skin defining an inside surface. The thermalmanagement system includes a heat exchanger assembly comprising astructural backing and a cooling unit, the structural backing configuredto mount the cooling unit in a position adjacent to, and in thermalcommunication with, the inside surface of the skin, the cooling unitformed of an elastic or semi-rigid material to conform to a shape of theinside surface of the skin.

These and other features, aspects and advantages of the presentinvention will become better understood with reference to the followingdescription and appended claims. The accompanying drawings, which areincorporated in and constitute a part of this specification, illustrateembodiments of the invention and, together with the description, serveto explain the principles of the invention.

BRIEF DESCRIPTION OF THE DRAWINGS

A full and enabling disclosure of the present invention, including thebest mode thereof, directed to one of ordinary skill in the art, is setforth in the specification, which makes reference to the appendedfigures, in which:

FIG. 1 is a top view of an aircraft in accordance with an exemplaryembodiment of the present disclosure.

FIG. 2 is a side view of the exemplary aircraft of FIG. 1.

FIG. 3 is cut-a-way, schematic view of a fuselage of the exemplaryaircraft of FIGS. 1 and 2.

FIG. 4 is a schematic, cross-sectional view of the fuselage of FIG. 3with a thermal management system in accordance with an exemplaryembodiment of the present disclosure.

FIG. 5 is a close-up, schematic view of a portion of the fuselage andthermal management system of FIG. 4.

FIG. 6 is a close-up, plan view of a portion of the fuselage and thermalmanagement system of FIG. 4.

FIG. 7 is a schematic, cross-sectional view of a cooling tube of a heatexchanger assembly of a thermal management system in accordance with anexemplary embodiment of the present disclosure.

FIG. 8 is a schematic, cross-sectional view of a heat exchanger assemblyof a thermal management system in accordance with an exemplaryembodiment of the present disclosure.

FIG. 9 is a schematic, cross-sectional view of a heat exchanger assemblyof a thermal management system in accordance with another exemplaryembodiment of the present disclosure.

FIG. 1010 is a schematic, cross-sectional view of a heat exchangerassembly in accordance with yet another exemplary embodiment of thepresent disclosure, viewed in the transverse and longitudinaldirections.

FIG. 11 is a schematic, cross-sectional view of the exemplary heatexchanger assembly of FIG. 10 taken along Line 11-11 in FIG. 10.

FIG. 12 is a schematic, cross-sectional view of a heat exchangerassembly of a thermal management system in accordance with yet anotherexemplary embodiment of the present disclosure.

FIG. 13 is a flow diagram of a method for attaching a heat exchangerassembly of a thermal management system to an inside surface of a skinof a vehicle in accordance with an exemplary aspect of the presentdisclosure.

FIG. 14 is a flow diagram of a method for operating a heat exchangerassembly of a thermal management system operable with an inside surfaceof a skin of a vehicle in accordance with an exemplary aspect of thepresent disclosure.

DETAILED DESCRIPTION

Reference will now be made in detail to present embodiments of theinvention, one or more examples of which are illustrated in theaccompanying drawings. The detailed description uses numerical andletter designations to refer to features in the drawings. Like orsimilar designations in the drawings and description have been used torefer to like or similar parts of the invention.

As used herein, the terms “first”, “second”, and “third” may be usedinterchangeably to distinguish one component from another and are notintended to signify location or importance of the individual components.

The terms “upstream” and “downstream” refer to the relative directionwith respect to fluid flow in a fluid pathway. For example, “upstream”refers to the direction from which the fluid flows, and “downstream”refers to the direction to which the fluid flows.

The terms “coupled,” “fixed,” “attached to,” and the like refer to bothdirect coupling, fixing, or attaching, as well as indirect coupling,fixing, or attaching through one or more intermediate components orfeatures, unless otherwise specified herein.

The singular forms “a”, “an”, and “the” include plural references unlessthe context clearly dictates otherwise.

Approximating language, as used herein throughout the specification andclaims, is applied to modify any quantitative representation that couldpermissibly vary without resulting in a change in the basic function towhich it is related. Accordingly, a value modified by a term or terms,such as “about”, “approximately”, and “substantially”, are not to belimited to the precise value specified. In at least some instances, theapproximating language may correspond to the precision of an instrumentfor measuring the value, or the precision of the methods or machines forconstructing or manufacturing the components and/or systems. Forexample, the approximating language may refer to being within a 10percent margin.

Referring now to the drawings, wherein identical numerals indicate thesame elements throughout the Figs., FIG. 1 provides a top view of anexemplary aircraft 10 as may incorporate various embodiments of thepresent disclosure. FIG. 2 provides a port side 24 view of the aircraft10 as illustrated in FIG. 1. As shown in FIGS. 1 and 2 collectively, theaircraft 10 defines a longitudinal direction L that extends generallyalong a longitudinal centerline 12 of the aircraft 10, a verticaldirection V, a transverse direction T, a forward end 14, and an aft end16.

Moreover, the aircraft 10 includes various structures, such as afuselage 20 extending longitudinally from the forward end 14 of theaircraft 10 towards the aft end 16 of the aircraft 10, and a pair ofwings 22, or rather, a first wing 22A and a second wing 22B. The firstwing 22A extends outwardly from the fuselage 20 generally along thetransverse direction T with respect to the longitudinal centerline 12,from the port side 24 of the fuselage 20. Further, the second wing 22Bsimilarly extends outwardly from the fuselage 20, generally along thetransverse direction T with respect to the longitudinal centerline 12,from a starboard side 26 of the fuselage 20. Each of the wings 22A, 22Bfor the exemplary embodiment depicted includes one or more leading edgeflaps 28 and one or more trailing edge flaps 30.

Referring still to the exemplary aircraft 10 of FIGS. 1 and 2, theaircraft 10 further includes additional structures, such as a verticalstabilizer 32 having a rudder flap 34 for yaw control, and a pair ofhorizontal stabilizers 36, each having an elevator flap 38 for pitchcontrol. Additionally, the aircraft 10 may include structures such asfairings, externally mounted sponsons or pods, tail cones, enginenacelles, etc.

However, it should be appreciated that in other exemplary embodiments ofthe present disclosure, the aircraft 10 may additionally oralternatively include any other suitable configuration of stabilizers orstructures that may or may not extend directly along the verticaldirection V or horizontal/transverse direction T. In addition,alternative stabilizers or structures may be any suitable shape, size,configuration, or orientation while remaining within the scope of thepresent subject matter.

Each of the above structures, such as the fuselage 20, wings 22A, 22B,and stabilizers 23, 36, additionally includes an outer skin 40. Theouter skin 40 may be formed of a thin sheet metal, composite material,thermally-conductive composite material, ceramic material, and/or othersuitable material.

The exemplary aircraft 10 of FIGS. 1 and 2 also includes a propulsionsystem. The exemplary propulsion system depicted includes a plurality ofaircraft engines, at least one of which mounted to each of the pair ofwings 22A, 22B. Specifically, the plurality of aircraft engines includesa first aircraft engine 42 mounted to the first wing 22A and a secondaircraft engine 44 mounted to the second wing 22B. In at least certainexemplary embodiments, the aircraft engines 42, 44 may be configured asturbofan jet engines suspended beneath the wings 22A, 22B in anunder-wing configuration.

Alternatively, however, in other exemplary embodiments any othersuitable aircraft engine may be provided. For example, in otherexemplary embodiments the first and/or second aircraft engines 42, 44may alternatively be configured as turbojet engines, turboshaft engines,turboprop engines, etc. Further, in still other exemplary embodiments,the propulsion system may include one or more electric, orhybrid-electric, aircraft engines (e.g., electric fans). In any of theabove embodiments, the engines may be arranged in any suitable manner(e.g., stabilizer-mounted, fuselage-mounted, etc.).

Further, for the embodiment shown the aircraft 10 additionally includesa thermal management system 100. As is depicted in phantom, the thermalmanagement system 100 includes a heat exchanger assembly 102 positionedadjacent to, and in thermal communication with, an inside surface of theouter skin 40 of the aircraft 10 (as will be explained in more detailbelow). Moreover, the thermal management system 100 includes a thermalbus 104 and at least one heat source exchanger 106. The heat sourceexchanger 106 may be located within, proximal to, or otherwise inthermal communication with, an aircraft engine (e.g., engines 42, 44),auxiliary power unit, energy storage unit, environmental control system,electrical power conditioner, aircraft avionics unit, payload avionicsunit, etc. More specifically, the exemplary thermal management system100 depicted includes a plurality of heat source exchangers 106, each ofthe plurality of heat source exchangers 106 thermally coupled to a heatsource of one of the engines 42, 44 (e.g., a lubrication oil heatsource, a cooled cooling air heat source, etc.). The thermal bus 104 maytransport a thermal fluid from the heat source exchangers 106 to theheat exchanger assembly 102 located adjacent to, and in thermalcommunication with, the inside surface of the outer skin 40 forrejecting heat from the heat sources of the engines 42, 44 using theheat exchanger assembly 102. In such a manner, the thermal managementsystem 100 may utilize an ambient airflow over an outer surface of theouter skin 42 reject heat from certain heat sources of the aircraft 10.

The “thermal fluid” may be any suitable fluid for transferring thermalenergy. For example, in at least certain exemplary embodiments thethermal fluid may be air (which has the benefit of being abundant andcan recharge cooling system to offset leakages); gasses other than air;liquids such as water, water-glycol mixtures (to, e.g., preventfreezing), oils including lubrication oil and thermal oils such asSyltherm, Dowtherm, etc.; fuel (allowing for, e.g., fuel cooling throughaircraft skin); refrigerants (including CO2, supercritical CO2, and/orany other refrigerant, such as those having an “R” designation from theAmerican Society of Heating, Refrigerating and Air-ConditioningEngineers); functional equivalents of any of the above; and/orcombinations of any of the above.

Referring now to FIG. 3, a partial, schematic, cutaway view of a sectionof the fuselage 20 of the aircraft 10 10 described above with referenceto FIGS. 1 and 2 is provided. As is shown, the fuselage 20 includes theouter skin 40, as well as a frame assembly 108 having a plurality ofstructural members. The fuselage 20 defines a circumferential directionC extending about the longitudinal centerline 12 of the aircraft 10.Further, the outer skin 40 defines an outside surface 110 exposed to theambient airflow over the aircraft 10 and an inside surface 112. Theplurality of structural members of the frame assembly 108 extend fromthe inside surface 112 of the outer skin 40. For the embodiment shown,the plurality of structural members of the frame assembly 108 includes aplurality of frame members 114 extending about the longitudinalcenterline 12 in the circumferential direction C and spaced from oneanother along the longitudinal direction L. Additionally, the pluralitystructural members of the frame assembly 108 includes a pluralitylongitudinal stiffeners 116 extending generally along the longitudinaldirection L. The plurality of longitudinal stiffeners 116 are spacedfrom one another along the circumferential direction C.

Referring now to FIG. 4 a schematic, cross-sectional view of thefuselage 20 of FIG. 3 is provided, taken generally along Line 4-4 ofFIG. 3. As was noted above, the fuselage 20 generally includes the frameassembly 108 having the plurality structural members extending generallyfrom the inside surface 112 of the outer skin 40. The pluralitystructural members includes a first structural member, a secondstructural member, a third structural member, and a fourth structuralmember. For the embodiment shown, the first structural member is a firstlongitudinal stiffener 116A, the second structural member is a secondlongitudinal stiffener 116B, the third structural member is a thirdlongitudinal stiffener 116C, and the fourth structural member is afourth longitudinal stiffener 116D. Each of these longitudinalstiffeners 116 extends generally along the longitudinal direction L andis spaced from one another generally along the circumferential directionC.

Moreover, as will be appreciated, the thermal management system 100 ofthe aircraft 10, briefly introduced above, includes the heat exchangerassembly 102 positioned adjacent to, and in thermal communication with,the inside surface 112 of the outer skin 40, and further positionedbetween the first structural member and the second structural member, ormore specifically, between the first longitudinal stiffener 116A and thesecond longitudinal stiffener 116B.

It will be appreciated, that as used herein, the term “positionedadjacent to, and in thermal communication with” refers to one componenteither contacting the other component, of being separated only by asmall number of intermediate components and/or air gaps notsubstantially impeding a thermal transfer from one component to theother. For example, as used herein, the term “positioned adjacent to,and in thermal communication with” may allow for, e.g., intermediatethermally conductive tapes or other adhesives, as well as otherthermally-conductive compounds (such as wax, grease, etc.) between twocomponents (see, e.g., FIG. 9) and/or air gaps resulting fromlimitations of commercially practical manufacturing methods (such as airgaps less than about 1 inch, such as less than about 0.5 inches, such asless than about 0.25 inches).

Referring still particularly to the exemplary embodiment shown in FIG.4, the heat exchanger assembly 102 generally includes a cooling unit anda structural backing 120. For the embodiment shown, the cooling unit isa cooling tube 118. The structural backing 120 mounts the cooling tube118 in position adjacent to, and in thermal communication with, theinside surface 112 of the outer skin 40. In such a manner, the coolingtube 118 may transfer heat from a thermal fluid flowing therethrough(received from, e.g., the thermal bus 104) across the outer skin 40 toan ambient airflow over the outer skin 40.

It will be appreciated, however, that in other embodiments, the coolingunit of the heat exchanger assembly 102 may be, e.g., a plate definingone or more internal passages, with the the plate having a geometry thatis conformal to and attached to the inside surface 112 of the outer skin40.

More specifically, referring still to the embodiment of FIG. 4, the heatexchanger assembly 102 is coupled to a first structural member, a secondstructural member, or both. Particularly for the embodiment of FIG. 4,the structural backing 120 is mounted to the first longitudinalstiffener 116A, the second longitudinal stiffener 116B, or both. Inparticular, for the embodiment shown, the structural backing 120 ismounted to both the first longitudinal stiffener 116A and the secondlongitudinal stiffener 116B.

Further, for the embodiment shown, the structural backing 120 utilizes ageometry of the first longitudinal stiffener 116A and secondlongitudinal stiffener 116B to mount the thermal heat exchanger assembly102. For example, referring now also to FIG. 5, providing a close-up,schematic view of the heat exchanger assembly 102 mounted to the outerskin 40, it will be appreciated that the outer surface of the fuselage20 defines a generally circular or ovular shape. As such, the localregion of the outer skin 40 depicted in FIGS. 4 and 5 generally definesan arcuate shape. The longitudinal stiffeners 116 extend generally fromthe inside surface 112 of the outer skin 40 in a generally perpendicularmanner, such that the longitudinal stiffeners 116 are not parallel toone another.

More particularly, the first and second longitudinal stiffeners 116A,116B are slanted towards one another as they extend from the insidesurface 112 of the outer skin 40. Referring particularly to FIG. 4, thefirst longitudinal stiffener 116A defines a first reference line 128extending away from the inside surface 112 of the outer skin 40 and thesecond longitudinal stiffener 116B defines a second reference line 130extending away from the inside surface 112 of the outer skin 40. Thefirst and second reference lines 128, 130, which are each straightlines, are not parallel to one another, and instead converge towards oneanother such that they contact one another.

Further, referring particularly to FIG. 5, the first and secondlongitudinal stiffeners 116A, 116B define a separation distance 122between their distal ends 124 (which is greater than a separationdistance at their respective bases proximate the inside surface 112 ofthe outer skin 40; not labeled). Further, the structural backing 120defines a length 126. The length 126 of the structural backing 120 isgreater than the separation distance 122 defined between the distal ends124 of the first and second longitudinal stiffeners 116A, 116B.

In such a manner, the structural backing 120 of the heat exchangerassembly 102 may be fixed at least partially between the firstlongitudinal stiffener 116A and second longitudinal stiffener 116B formounting the heat exchanger assembly 102. More specifically, thestructural backing 120 may be wedged into place to mount the heatexchanger assembly 102.

It will be appreciated, however, that in other exemplary embodiments,the structural backing 120 instead be fixed to the longitudinalstiffeners 116, or other structural features (such as the frame members114) of the frame assembly 108 of the fuselage 20 (or other structure ofthe aircraft 10) in any other suitable manner, such as through asuitable bolting, clamping, bonding, or other suitable attachment means.

Referring still to FIG. 4, it will be appreciated that for theembodiment shown, the thermal management system 100 further includes aplurality of heat exchanger assemblies 102. In particular, theabove-described heat exchanger assembly 102 is a first heat exchangerassembly 102A, and the thermal management system 100 further includes asecond heat exchanger assembly 102B and a third heat exchanger assembly102C. The second heat exchanger assembly 102B is positioned adjacent to,and in thermal communication with, the inside surface 112 outer skin 40at a location between the second longitudinal stiffener 116B and thirdlongitudinal stiffener 116C, and the third heat exchanger assembly 102Cis positioned adjacent to, and in thermal communication with, the insidesurface 112 of the outer skin 40 at a location between the thirdlongitudinal stiffener 116C and the fourth longitudinal stiffener 116D.For the exemplary embodiment shown, the first exchanger assembly isfluidly coupled to the second heat exchanger assembly 102B through afirst jumper line 132, and similarly, the third heat exchanger assembly102C is fluidly coupled to the second heat exchanger assembly 102Bthrough a second jumper line 134. In such a manner, it will beappreciated that the first heat exchanger assembly 102A, the second heatexchanger assembly 102B, and the third heat exchanger assembly 102C arearranged in serial flow order.

However, in other exemplary embodiments, one or more of the first heatexchanger assembly 102A, the second heat exchanger assembly 102B, andthe third heat exchanger assembly 102C may instead be arranged in aparallel flow order or a combination of parallel and series flow order.Further, in other exemplary embodiments, the thermal management system100 may include any suitable number of heat exchanger assemblies 102,such as one, two, four, etc.

Further, referring briefly to FIG. 6, a plan view of a portion of thefirst heat exchanger assembly 102A is depicted. Specifically, FIG. 6depicts the cooling tube 118 of the first heat exchanger assembly 102A.The structural backing 120 of the first heat exchanger assembly 102A isremoved for clarity. As is shown, the cooling tube 118 of the first heatexchanger assembly 102A extends in a serpentine path in order to, e.g.,maximize a contact with the inside surface 112 of the outer skin 40. Thecooling tube 118 defines an inlet 136 and an outlet 138. The inlet 136may be in flow communication with the thermal bus 104 (see, e.g., FIG.1), and the outlet 138 may be in flow communication with, e.g., thefirst jumper line 132.

For the embodiment depicted in FIG. 6, it will be appreciated that thefirst heat exchanger assembly 102A is positioned generally between thefirst longitudinal stiffener 116A and the second longitudinal stiffener116B, as well as between a first frame member 114A and a second framemember 114B, spaced along the longitudinal direction L.

Moreover, referring now to FIG. 7, a cross-sectional view of a portionof the fuel cooling tube 118 of the first heat exchanger assembly 102Ais depicted, taken along Line 7-7 in FIG. 6. As is shown, the portion ofthe cooling tube 118 depicted extends along a lengthwise direction LWand defines a first side 140 proximate the inside surface 112 of theouter skin 40 and a second side 142 opposite the first side 140. For theembodiment shown, the cooling tube 118 defines a plurality of nonlinearfeatures spaced along the lengthwise direction LW of the first side 140.The nonlinear features may assist with creating increased heat transferbetween the thermal fluid flowing through the cooling tube 118 and theouter skin 40 of the aircraft 10, and thus between the thermal fluidflowing through the cooling tube 118 and an ambient airflow over theouter surface of the aircraft 10.

For the embodiment of FIG. 7, the nonlinear features include a pluralityof dimples 144 having a generally semicircular shape. However, in otherexemplary embodiments, any other suitable nonlinear features may beprovided to enhance thermal transfer. For example, In other exemplaryembodiments, the cooling tube 118 may include any suitable combinationof turbulators, dimples, grooves (such as spiral grooves), etc.

Notably, for the embodiment of FIG. 7, each of the plurality ofnonlinear features are positioned on the first side 140 of the coolingtube 118 proximate the inside surface 112. It will be appreciated,however, that in other embodiments, the cooling tube 118 may have anyother suitable non-linear feature arranged in any suitable manner, andpositioned at any other suitable location. For example, in otherembodiments, the cooling tube 118 may further include nonlinear featureson the second side 142 of the cooling tube 118, or elsewhere.

It will be appreciated, that as used herein, the term “nonlinearfeature,” with reference to the cooling tube 118, refers to any section,or portion, of the cooling tube 118 that does not extend substantiallylinearly along the lengthwise direction LW of the cooling tube 118.

In order to form the cooling tube 118 having such nonlinear features,the cooling tube may be additively manufactured, also known as 3-Dprinted. However, in other embodiments, the cooling tube 118 may not beadditively manufactured, and instead may be formed in any suitablemanner, such as by metal sheet stamping and diffusion bonding.

Referring now to FIG. 8, a close-up, cross-sectional view of a heatexchanger assembly 102 in accordance with an embodiment of the presentdisclosure is provided. The heat exchanger assembly 102 of FIG. 8 isdepicted in the same viewing plane as the heat exchanger assembly 102described above with reference to FIG. 4.

In certain embodiments, the heat exchanger assembly 102 of FIG. 8 may beconfigured in substantially the same manner as the exemplary heatexchanger assembly 102 described above with reference to FIG. 4. Forexample, as is shown, the heat exchanger assembly 102 generally includesa structural backing 120 and a cooling unit. For the embodimentdepicted, the cooling unit is a cooling tube 118. The cooling tube 118is mounted by the structural backing 120 adjacent to, and in thermalcommunication with, the inside surface 112 of the outer skin 40 of thevehicle. Further, the cooling tube 118 is configured to flow a thermalfluid therethrough to transfer heat from the thermal fluid through theouter skin 40 of the vehicle to an ambient airflow over the outer skin40 of the vehicle.

As will be appreciated from the view of FIG. 8, the inside surface 112of the outer skin 40 the vehicle defines a nonplanar geometry, such asan arcuate geometry. In order to maximize a heat transfer from thethermal fluid through the cooling tube 118 to the outer skin 40 of thevehicle, the cooling tube 118 is configured to form to a geometry of theinside surface 112 of the outer skin 40. As such, the cooling tube 118is formed of a flexible or semirigid material.

For example, in the embodiment depicted, the cooling tube 118 is formedof a composite having an additive for increased thermal conductivity.For example, the cooling tube 118 may be formed of a filled polymermaterial. The term “filled polymer” refers to a natural or syntheticpolymeric material having thermally conductive particles therein toallow a desired amount of heat transfer across the material. Forexample, the cooling tube 118 may be formed of a polymer, such asrubber, having aluminum particles, iron particles, magnesium oxideparticles, aluminum nitride particles, boron nitride particles, diamonddust, carbon dust, carbon nanotubes, carbon fiber filaments, or acombination thereof, therein. Further, it will be appreciated that asused herein, that the term “flexible or semi-rigid,” as used to describethe cooling tube 118, refers to being formed of a material capable of atleast partially elastically deforming to conform to a geometry of theinside surface 112 of the outer skin 40 when the heat exchanger assembly102 is installed.

As such, the cooling tube 118 may be formed of a material capable ofconforming to the geometry of the inside surface 112 of the skin 40,while still being capable of transferring a desired amount of heat fromthe thermal fluid flowing therethrough to the skin 40.

Further, referring still to FIG. 8, in order to provide the desiredcontact between the cooling tube 118 and the inside surface 112 of theouter skin 40, the heat exchanger assembly 102 further includes aninflatable member 150 operable with the cooling tube 118 to press thecooling tube 118 towards the inside surface 112 of the outer skin 40.Specifically, for the embodiment shown, the inflatable member 150 is aninflatable bladder positioned at least partially within the cooling tube118. The inflatable bladder may run lengthwise within cooling tube 118(e.g., along the lengthwise direction LW of the cooling tube 118, as isdepicted in FIG. 7).

In at least certain exemplary embodiments, the inflatable bladder mayreceive a compressed gas flow once the heat exchanger assembly 102 isinstalled to press the cooling tube 118 towards the inside surface 112of the outer skin 40. In such a manner, it will be appreciated that inat least certain exemplary aspects, inflatable bladder may be at leastpartially deflated (as is depicted in phantom FIG. 8 as 150′) when theheat exchanger assembly 102 is installed, allowing for increased ease ofinstallation. Further, in at least certain exemplary aspects, theinflatable member 150 may be deflated during certain operationalconditions, non-operational conditions, and/or maintenance activities.Such may protect the outer skin 40 and may further allow for increaseease of such maintenance activities.

The pressurized gas flow provided to the inflatable bladder may comefrom, e.g., an engine bleed, an onboard gas container, a refrigerantbleed from a vapor-compression cycle refrigeration unit, a groundsource, etc. The temperature of the pressurized gas flow may be reducedby some means such as a heat exchanger, throttling process, or otherprecooling means to further assist with a cooling of a thermal fluidthrough the heat exchanger assembly 102. In at least certain exemplaryembodiments, the inflatable bladder may extend substantially along theentire length of the cooling tube 118 (e.g., substantially along theentire length between an inlet 136 and an outlet 138 of the cooling tube118; see, e.g., FIG. 6).

Notably, inflating the inflatable bladder once the heat exchangerassembly 102 is installed may further assist with the mounting of theheat exchanger assembly 102, and further wedging the structural backing120 between adjacent longitudinal stiffeners 116.

Referring still FIG. 8, it will be appreciated that the thermalmanagement system 100 may additionally include certain additionalfeatures for further removing heat from the thermal transfer fluidflowing through the cooling tube 118. Specifically, for the embodimentshown, thermal management system 100, or rather, the heat exchangerassembly 102, further defines a cooling air flowpath 152 adjacent to,and in thermal communication with, the cooling tube 118. For theembodiment shown, the cooling air flowpath 152 is defined by thestructural backing 120, the cooling tube 118, the inside surface 112 ofthe outer skin 40, or combination thereof. Specifically, for theembodiment shown, the cooling air flowpath 152 is defined by each of thestructural backing 120, the cooling tube 118, and the inside surface 112of the outer skin 40. Further, the thermal management system 100comprises a cooling airflow delivery system 154 and a cooling airflowexhaust system 156. In at least certain exemplary embodiments, thecooling airflow delivery 154 system includes a cooling airflow source158 and a cooling airflow delivery conduit 160. The cooling airflowsource 158 may be, e.g., a cabin air source or other suitable relativelycool airflow source. Further, the cooling airflow exhaust system 156generally includes a cooling airflow exhaust conduit 162 and a coolingairflow sink 164. The cooling airflow sink 164 may be, e.g., an exhaustto an ambient location.

Alternatively, in other embodiments, the cooling airflow exhaust 164 maybe in airflow communication with the cooling airflow source 158 through,e.g., an airflow heat exchanger. In such an embodiment, the coolingairflow channels 152 may be configured as a closed loop airflow coolingsystem.

It will be appreciated, however, that in other exemplary embodiments,the heat exchanger assembly 102 may have still other suitableconfigurations. For example, referring now to FIG. 9, a heat exchangerassembly 102 in accordance with another exemplary embodiment of thepresent disclosure is provided. In the embodiment of FIG. 9, the heatexchanger assembly 102 may be configured in substantially the samemanner as the heat exchanger assembly 102 described above with referenceto FIG. 8.

For example, the exemplary heat exchanger assembly 102 depicted in FIG.9 generally includes a structural backing 120 and a cooling unit. Forthe embodiment depicted, the cooling unit is a cooling tube 118. Thecooling tube 118 is positioned adjacent to, and in thermal communicationwith, the inside surface 112 of the outer skin 40 for transferring heatfrom a thermal fluid flowing through the cooling tube 118, across theouter skin 40, to an ambient airflow over the outer skin 40. Further,the heat exchanger assembly 102 depicted in FIG. 9 includes aninflatable member 150 operable with the cooling tube 118 to the pressthe cooling tube 118 towards the inside surface 112 of the outer skin40.

However, for the exemplary embodiment of FIG. 9, the inflatable member150 is not located within the cooling tube 118, and instead ispositioned between the cooling tube 118 and the structural backing 120.More specifically, for the embodiment shown, the heat exchanger assembly102 further includes a load applicator 166 positioned between theinflatable member 150 and the cooling tube 118, as well as a firststandoff member 168 and a second standoff member 170. For the embodimentshown, the first and second standoff members 168, 170 are resilientmembers, or springs, and extend from the load applicator 166 towardsinside surface 112 of the outer skin 40. For the embodiment shown, thefirst and second standoff members 168, 170 are positioned on opposingsides of the first cooling tube 118 (e.g., along the circumferentialdirection C). The first and second standoff members 168, 170 may ensurea desired alignment of the cooling tube 118 with the inside surface 112112 of the outer skin 40.

It will be appreciated, however, that in other exemplary embodiments,the first and second standoff members 168, 170 may be configured in anysuitable manner. For example, in other exemplary embodiments, the firstand/or second standoff member 168, 170 may be configured as a spring,such as a standard helical spring. With one or more of theseconfigurations, the first and second standoff members 168, 170 may actto align the heat exchanger assembly 102 with the inside surface 112 ofthe outer skin 40.

Further for the embodiment shown, the load applicator 166 defines achannel 172, with the inflatable member 150 positioned at leastpartially within the channel 172. The inflatable member 150, as with theinflatable bladder discussed above, is configured to increase in volumewhen a pressurized airflow is provided thereto. As such, the inflatablemember 150 may be deflated, as is depicted in phantom FIG. 9 as 150′,during installation of the heat exchanger assembly 102, and subsequentlyinflated after installation of the heat exchanger assembly 102. Theincrease in volume of the inflatable member 150 may act to both pressthe cooling tube 118 against the inside surface 112 of the outer skin40, to assist with molding the cooling tube 118 to the geometry of theinside surface 112 of the outer skin 40, and further to assist withinstallation of the heat exchanger assembly 102. In particular, theinflatable member 150 may be deflated during installation to allow forthe heat exchanger assembly 102 to be moved into position betweenadjacent structural members (e.g., adjacent longitudinal stiffeners116A, 116B; see FIG. 4) with relative ease, and then subsequentlyinflated to wedge the structural backing 120 in between adjacentstructural members (e.g., adjacent longitudinal stiffeners 116A, 116B;see FIG. 4).

As is further depicted in FIG. 9, the heat exchanger assembly 102additionally includes an adhesive 174 between the inside surface 112 ofthe outer skin 40 and at least one of the first standoff member 168, thesecond standoff member 170, or the cooling tube 118. Specifically, forthe embodiment shown, the heat exchanger assembly 102 includes adhesive174 between each of the inside surface 112 of the outer skin 40 and thefirst standoff member 168, the second standoff member 170, and thecooling tube 118. Such may assist with installation of the heatexchanger assembly 102 by allowing the heat exchanger assembly 102 totemporarily mounted in position using the adhesive 174 and to remain inposition while, e.g., the inflatable member 150 is inflated and thestructural backing 120 is attached to the structural members of thefuselage 20, e.g., wedged between adjacent first and second longitudinalstiffeners 116A, 116B.

In certain exemplary embodiments, the adhesive 174 may be a thermallyconductive adhesive. For example, the adhesive 174 may be a double-sidedtape, glue, etc. The adhesive 174 may have a thermal conductivitygreater than about 1.0 Watts/meter-Kelvin, such as greater than about1.5 Watts/meter-Kelvin.

It will further be appreciated that the configuration of FIG. 9 mayfurther assist with accommodating relative thermal growth andcontraction during operation of the aircraft 10. In particular, theadhesive may assist with accommodating relative thermal growth andcontraction during operation of the aircraft 10

Referring now to FIGS. 10 and 11, close-up, cross-sectional views of aheat exchanger assembly 102 in accordance with yet an embodiment of thepresent disclosure are provided.

In particular, it will be appreciated that for the embodiment depicted,the heat exchanger assembly 102 includes a structural backing 120extending along a longitudinal direction L between two structuralmembers, and in particular between a first frame member 114A and asecond frame member 114B (FIG. 10). In addition, the structural backing120 extends across a plurality of structural members arrangedsubstantially perpendicularly to the first and second frame members114A, 114B, and more specifically, extends across a plurality oflongitudinal stiffeners 116 (i.e., stiffeners 116A, 116B, 116C for theembodiment depicted in FIG. 11).

Referring particularly to FIG. 10, the structural backing 120 is coupledto the first frame member 114A, the second frame member 114B, or both.Specifically, for the embodiment shown, the structural backing 120 iscoupled to the first frame member 114A. For the embodiment shown, thestructural backing 120 is coupled to the first frame member 114A througha mechanical fastener 175. However, in other embodiments, the structuralbacking 120 may be coupled to the first frame member 114A in any othersuitable manner.

Further, referring particularly to FIG. 11, it will be appreciated thatfor the exemplary heat exchanger assembly 102 depicted, the structuralbacking 120 is shaped to accommodate the various structural members ofthe structure within which the heat exchanger assembly 102 is installed.More specifically, for the embodiment shown the structural backing 120defines a corrugated shape. More specifically still, the structuralbacking 120 includes a plurality of near sections 176 defining a firstseparation distance 178 from the inside surface 112 of the outer skin 40and a plurality of far sections 180 defining a second separationdistance 182 from the inside surface 112 of the outer skin 40. The firstseparation distance 178 is less than the second separation distance 182,such as at least about 10% less, such as at least about 20% less, suchas up to about 90% less.

Further for the embodiment depicted, the corrugated shape of thestructural backing 120 allows for the structural backing 120 to hold thecooling unit of the heat exchanger assembly 102 in position adjacent to,and in thermal communication with, the inside surface 112 of the skin40. In particular, for the embodiment depicted in FIG. 11, the coolingunit of the heat exchanger assembly 102 is a cooling bladder 184extending over a plurality of structural members, and in particularextending across longitudinal stiffeners 116A, 116B, 116C for theembodiment depicted in FIG. 11. For this embodiment, the near sections176 of the structural backing 120 press the cooling bladder 184 towardthe inside surface 112 of the skin 40 and the far sections 180 allowportions of the cooling bladder 184 to extend over the structuralmembers.

Further still for the embodiment depicted, the cooling unit, or coolingbladder 184 for the embodiment shown, additionally includes a pluralityof inflatable members 150 for pressing the cooling bladder 184 againstthe inside surface 112 of the skin 40, to increase a heat fluxtherebetween.

However, in other embodiments, the heat exchanger assembly 102 may havestill other configurations. For example, referring now to FIG. 12, aclose-up, cross-sectional view of a heat exchanger assembly 102 inaccordance with yet another embodiment of the present disclosure isprovided. The heat exchanger assembly 102 depicted in FIG. 12 may beconfigured in a similar manner as the heat exchanger assembly 102 ofFIG. 11. However, for the embodiment depicted, the heat exchangerassembly 102 includes a plurality of cooling units, or rather aplurality of cooling bladders 184, with each cooling bladder 184positioned between adjacent structural members, such as between adjacentlongitudinal stiffeners 116A, 116B, 116C.

It will be appreciated that although the exemplary thermal managementsystems 100 described above are described with reference to a fuselage20 of an aircraft 10, in other exemplary embodiments the heat exchangerassembly(ies) of the thermal management system 100 may additionally oralternatively be positioned adjacent to, and in thermal communicationwith, an inside surface of a skin of any suitable structures of anaircraft 10. For example, in other exemplary embodiments, the thermalmanagement system 100 may include one or more heat exchangersincorporated into a wing of an aircraft 10, a stabilizer of an aircraft10, or additional structures, such as fairings, externally-mountedsponsons or pods, tail cones, engine nacelles, etc. For example, withrespect to the wing configuration, the structural members may be a wingspar, nose ribs, rear ribs, etc. Additionally with such a configuration,the longitudinal and circumferential directions may be relative to thewing structure.

Further, in still other exemplary embodiments, the thermal managementsystem 100 may be operable with other vehicles, such as marine vehicles(e.g., boats, submarines, etc.), land vehicles, space vehicles, etc.

In one or more of these embodiments, a heat exchanger assembly may bemounted between structural members that are relatively parallel to oneanother, such that they do not converge towards one another. In suchcases, a structural backing of the heat exchanger assembly may becoupled to one or both of the structural members through any othersuitable means, such as by bolting or other mechanical fastening,arrangement of complementary geometries (e.g., hooks, loops, ledges,etc.), adhesives, etc.

It will further be appreciated that although for the embodimentsdescribed above the heat exchanger assembly(ies) are described as beinga heat sink heat exchanger to transfer heat from a thermal fluid throughan outer skin to an ambient flow, in other embodiments, the heat fluxmay be reversed. For example, with certain configurations, the heatexchanger assembly(ies) of the thermal management system may beconfigured to absorb heat from the outer skin of the structure of thevehicle to reduce a temperature of the outer skin of the structure ofthe vehicle. For example, such may be incorporated into a supersonic orhypersonic aircraft to cool an outer skin of a structure of suchaircraft.

Referring now to FIG. 13, a method 300 of attaching a heat exchangerassembly of a thermal management system to an inside surface of the skinof the vehicle is provided. The heat exchanger assembly and thermalmanagement system may be configured in any suitable manner. For example,in certain exemplary embodiments, the heat exchanger assembly in thermalmanagement system may be configured in accordance with one or more theexemplary embodiments described above with reference to FIGS. 1 through12. However, in other embodiments, the heat exchanger assembly andthermal management system may instead be configured in or as any othersuitable manner.

The heat exchanger assembly and thermal management system may beattached to an inside surface of a skin of a structure of a vehicle.

The exemplary method 300 includes at (302) positioning a heat exchangerassembly adjacent to, and thermal communication with, the inside surfaceof the skin the vehicle at a location between a first structural memberand a second structural member of the structure.

The exemplary method 300 further includes at (304) providing a flow ofgas to an inflatable bladder operable with the cooling tube of the heatexchanger assembly to press the cooling tube towards the inside surfaceof the skin.

Referring now to FIG. 14, a method 400 of operating a heat exchangerassembly of a thermal management system operable with an inside surfaceof the skin of the vehicle is provided. The heat exchanger assembly andthermal management system may be configured in any suitable manner. Forexample, in certain exemplary embodiments, the heat exchanger assemblyin thermal management system may be configured in accordance with one ormore the exemplary embodiments described above with reference to FIGS. 1through 12. However, in other embodiments, the heat exchanger assemblyand thermal management system may instead be configured in or as anyother suitable manner.

The heat exchanger assembly and thermal management system may beattached to an inside surface of a skin of a structure of a vehicle. Inparticular, the heat exchanger assembly may be positioned adjacent to,and thermal communication with, the inside surface of the skin thevehicle.

The exemplary method 400 includes at (402) providing a flow of gas to aninflatable member operable with a cooling unit of the heat exchangerassembly to press cooling unit towards the inside surface of the skin.Additionally, the method 400 includes at (404) determining a conditionof the vehicle, of the thermal management system, or both; and at (406)modifying a pressure within the inflatable member in response to thedetermined condition of the vehicle, of the thermal management system,or both.

For the exemplary aspect depicted, the condition determined at (404) maybe an operating condition of the vehicle, of the thermal managementsystem, or both. For example, the condition may be indicative of aflight stage of the aircraft (e.g., takeoff, climb, cruise, descent,taxi, etc.), whether or not one or more of the engines are operating andat what power level they are operating, whether or not the thermalmanagement system is operating, a speed at which the aircraft isoperating (e.g., subsonic, supersonic, hypersonic), etc.

Also for the exemplary aspect depicted, modifying the pressure withinthe inflatable member at (406) may include at (408) at least partiallydeflating the inflatable member or at (410) at least partially inflatingthe inflatable member. In such a manner, the method 400 may control apressure the inflatable member applies to the heating unit of the heatexchanger assembly based at least in part on the one or more conditionsof the vehicle, the thermal management system, or both in order toprovide a desired amount of heat transfer when desired, without damagingthe skin of the vehicle.

Further aspects of the invention are provided by the subject matter ofthe following clauses:

1. A vehicle including a structure including a skin defining an outsidesurface exposed to ambient cooling flow and an inside surface, thestructure including a first structural member extending from the insidesurface of the skin and a second structural member extending from theinside surface of the skin; and a thermal management system including aheat exchanger assembly positioned adjacent to, and in thermalcommunication with, the inside surface of the skin, the heat exchangerassembly positioned at least partially between the first and secondstructural members of the structure.

2. The vehicle of any of these clauses wherein the vehicle is anaircraft, and wherein the structure is a fuselage of the aircraft.

3. The vehicle of any of these clauses wherein the aircraft defines alongitudinal direction, wherein the first structural member is a firstlongitudinal stiffener extending generally along the longitudinaldirection, and wherein the second structural member is a secondlongitudinal stiffener extending generally along the longitudinaldirection.

4. The vehicle of any of these clauses wherein the first longitudinalstiffener defines a first reference line extending away from the insidesurface of the skin, wherein the second longitudinal stiffener defines asecond reference line extending away from the inside surface of theskin, wherein the first and second reference lines converge towards oneanother, and wherein the heat exchanger assembly includes a structuralbacking fixed at least partially between the first and secondlongitudinal stiffeners for mounting the heat exchanger assembly.

5. The vehicle of any of these clauses wherein the heat exchangerassembly is coupled to the first and second structural members of thestructure.

6. The vehicle of any of these clauses wherein the heat exchangerassembly includes a structural backing and a cooling tube, wherein thestructural backing mounts the cooling tube in position adjacent to, andin thermal communication with, the inside surface of the skin.

7. The vehicle of any of these clauses wherein the structural backing ismounted to the first structural member, the second structural member, orboth.

8. The vehicle of any of these clauses wherein the cooling tube isformed of a flexible or semi rigid material.

9. The vehicle of any of these clauses wherein the cooling tube isformed of a composite having an additive for increased thermalconductivity.

10. The vehicle of any of these clauses wherein the cooling tube isformed of a filled polymer material.

11. The vehicle of any of these clauses wherein the heat exchangerassembly further includes an inflatable member operable with the coolingtube to press the cooling tube towards the inside surface of the skin.

12. The vehicle of any of these clauses wherein the inflatable member isan inflatable bladder positioned at least partially within the coolingtube.

13. The vehicle of any of these clauses wherein the inflatable member ispositioned outside cooling tube between the cooling tube and thestructural backing.

14. The vehicle of any of these clauses wherein the heat exchangerassembly further includes a load applicator positioned betweeninflatable member and the cooling tube, a first standoff member, and asecond standoff member, and wherein the first and second standoffmembers are positioned on opposing sides of the cooling tube and extendfrom the load applicator towards the inside surface of the skin.

15. The vehicle of any of these clauses wherein the heat exchangerassembly defines a cooling air passage between the first standoffmember, the cooling tube, and the inside surface of the skin.

16. The vehicle of any of these clauses wherein the heat exchangerassembly includes a thermally conductive substance between the insidesurface of the skin and at least one of the first standoff member, thesecond standoff member, or the cooling tube.

17. The vehicle of any of these clauses wherein the heat exchangerassembly includes a thermally conductive adhesive between the insidesurface of the skin and at least one of the first standoff member, thesecond standoff member, or the cooling tube.

18. The vehicle of any of these clauses wherein the cooling tube isarranged in a serpentine pattern adjacent to the inside surface of theskin.

19. The vehicle of any of these clauses wherein the structure furtherincludes a third structural member extending from the inside surface ofthe skin, wherein the heat exchanger assembly is a first heat exchangerassembly, wherein the thermal management system further includes asecond heat exchanger assembly, wherein the second heat exchangerassembly is positioned adjacent to, and in thermal communication with,the inside surface of the skin at a location between the second andthird structural members of the structure, and wherein the first heatexchanger assembly is fluidly coupled to the second heat exchangerassembly.

20. The vehicle of any of these clauses wherein the heat exchangerassembly a cooling tube, and wherein the heat exchanger assembly definesa cooling air flowpath adjacent to, and in thermal communication with,the cooling tube.

21. The vehicle of any of these clauses wherein the heat exchangerassembly includes a cooling tube, wherein the cooling tube extends alonga lengthwise direction and defines a first side proximate the insidesurface of the skin and a second side opposite the first side, andwherein the cooling tube defines a plurality of nonlinear featuresspaced along the lengthwise direction on the first side.

22. The vehicle of any of these clauses further including:

an engine, wherein the thermal management system of the vehicle isthermally coupled to a heat source of the engine for rejecting heat fromthe heat source using the heat exchanger assembly.

23. The vehicle of any of these clauses wherein the first structuralmember is a first frame member, wherein the second structural member isa second frame member, wherein the thermal management system includes astructural backing and a cooling unit, wherein the cooling unit isformed of an elastic or semi-rigid material to conform to a shape of theinside surface of the skin.

24. The vehicle of any of these clauses wherein the cooling unit is acooling bladder configured to flow a thermal fluid therethrough.

25. The vehicle of any of these clauses wherein structure furtherincludes a longitudinal stiffener extending between the first and secondframe members, and wherein the cooling unit extends across thelongitudinal stiffener.

26. A thermal management system for a vehicle, the vehicle including astructure having a skin defining an inside surface, a first structuralmember extending from the inside surface of the skin, and a secondstructural member extending from the inside surface of the skin, thethermal management system including: a heat exchanger assembly includinga structural backing and a cooling tube, the structural backingconfigured to be mounted to the first structural member, the secondstructural member, or both, the structural backing further configured tomount the cooling tube in a position adjacent to, and in thermalcommunication with, the inside surface of the skin at a location betweenthe first and second structural members.

27. A thermal management system for a vehicle, the vehicle including astructure having a skin defining an inside surface, the thermalmanagement system including: a heat exchanger assembly including astructural backing and a cooling unit, the structural backing configuredto mount the cooling unit in a position adjacent to, and in thermalcommunication with, the inside surface of the skin, the cooling unitformed of an elastic or semi-rigid material to conform to a shape of theinside surface of the skin.

28. The thermal management system of any of these clauses the coolingunit is a cooling tube.

29. The thermal management system of any of these clauses the coolingtube is formed of a composite having an additive for increased thermalconductivity.

30. The thermal management system of any of these clauses the heatexchanger assembly further includes an inflatable member operable withthe cooling tube to press cooling tube towards the inside surface of theskin.

31. The thermal management system of any of these clauses the inflatablemember is an inflatable bladder positioned at least partially within thecooling tube.

32. The thermal management system of any of these clauses the inflatablemember is positioned outside the cooling tube and between the coolingtube and the structural backing.

33. The thermal management system of any of these clauses the heatexchanger assembly further includes a load applicator positioned betweenthe inflatable member and the cooling tube, a first standoff member, anda second standoff member, and wherein the first and second standoffmembers are positioned on opposing sides of the cooling tube and extendfrom the load applicator towards the inside surface of the skin.

34. The thermal management system of any of these clauses the heatexchanger assembly defines a cooling air passage between the firststandoff member, the cooling tube, and the inner surface of the skin.

35. The thermal management system of any of these clauses the heatexchanger assembly includes a thermally conductive adhesive between theinner surface of the skin and at least one of the first standoff member,the second standoff member, or the cooling tube.

36. The thermal management system of any of these clauses the coolingunit is a cooling bladder.

37. The thermal management system of any of these clauses the structureof the vehicle includes a structural member, and wherein the coolingbladder is configured to extend across the structural member.

38. The thermal management system of any of these clauses the structuralmember is a longitudinal stiffener, wherein the structure of the vehiclefurther includes a first frame member and a second frame member, whereinthe longitudinal stiffener extends between the first and second framemembers, wherein the structural backing is coupled to the first framemember and the second frame member.

39. The thermal management system of any of these clauses the heatexchanger assembly further includes an inflatable member operable withthe cooling bladder to press cooling bladder towards the inside surfaceof the skin.

40. The thermal management system of any of these clauses the heatexchanger assembly further includes a plurality of inflatable membersoperable with the cooling bladder to press cooling bladder towards theinside surface of the skin.

41. The thermal management system of any of these clauses each of theplurality of inflatable members are positioned within the coolingbladder.

42. The thermal management system of any of these clauses the structuralbacking defines a corrugated shape having a plurality of near sectionand far sections relative to the outer skin.

43. A vehicle including: a structure including a skin defining anoutside surface exposed to ambient cooling flow and an inside surface;and a thermal management system including a heat exchanger assemblyincluding a structural backing and a cooling tube, the structuralbacking mounting the cooling tube in a position adjacent to, and inthermal communication with, the inside surface of the skin, the coolingtube formed of an elastic or semi-rigid material conforming to a shapeof the inside surface of the skin.

44. A method of operating a heat exchanger assembly of a thermalmanagement system operable with an inside surface of a skin of a vehicleincluding: providing a flow of gas to an inflatable member operable witha cooling unit of the heat exchanger assembly to press cooling unittowards the inside surface of the skin.

45. The method of any of these clauses further including: positioning aheat exchanger assembly adjacent to, and in thermal communication with,the inside surface of the skin of the vehicle at a location between afirst structural member and a second structural member of the structureprior to providing the flow of gas to the inflatable member.

46. The method of any of these clauses further including: determining acondition of the vehicle, of the thermal management system, or both; andmodifying a pressure within the inflatable member in response to thedetermined condition of the vehicle, of the thermal management system,or both.

47. The method of any of these clauses wherein the condition is anoperating condition of the vehicle, of the thermal management system, orboth.

48. The method of any of these clauses wherein modifying the pressurewithin the inflatable member includes at least partially deflating theinflatable member.

49. The method of any of these clauses wherein modifying the pressurewithin the inflatable member includes providing the flow of gas to theinflatable member operable with the cooling unit of the heat exchangerassembly to press cooling unit towards the inside surface of the skin.

50. The thermal management system of any preceding clause wherein thethermal fluid is air, a gas other than air; a liquid such as water,water-glycol mixtures, an oil such as a lubrication oil and/or thermaloil such as Syltherm, Dowtherm, etc.; fuel; a refrigerant (includingCO2, supercritical CO2, and/or any other refrigerant, such as thosehaving an “R” designation from the American Society of Heating,Refrigerating and Air-Conditioning Engineers); a functional equivalentof any of the above; and/or a combination of any of the above.

This written description uses examples to disclose the invention,including the best mode, and also to enable any person skilled in theart to practice the invention, including making and using any devices orsystems and performing any incorporated methods. The patentable scope ofthe invention is defined by the claims, and may include other examplesthat occur to those skilled in the art. Such other examples are intendedto be within the scope of the claims if they include structural elementsthat do not differ from the literal language of the claims, or if theyinclude equivalent structural elements with insubstantial differencesfrom the literal languages of the claims.

What is claimed is:
 1. A vehicle comprising: a structure comprising askin defining an outside surface exposed to ambient cooling flow and aninside surface, the structure comprising a first structural memberextending from the inside surface of the skin and a second structuralmember extending from the inside surface of the skin; and a thermalmanagement system including a heat exchanger assembly positionedadjacent to, and in thermal communication with, the inside surface ofthe skin, the heat exchanger assembly positioned at least partiallybetween the first and second structural members of the structure.
 2. Thevehicle of claim 1, wherein the vehicle is an aircraft, wherein thestructure is a fuselage of the aircraft, wherein the aircraft defines alongitudinal direction, wherein the first structural member is a firstlongitudinal stiffener extending generally along the longitudinaldirection, and wherein the second structural member is a secondlongitudinal stiffener extending generally along the longitudinaldirection.
 3. The vehicle of claim 2, wherein the first longitudinalstiffener defines a first reference line extending away from the insidesurface of the skin, wherein the second longitudinal stiffener defines asecond reference line extending away from the inside surface of theskin, wherein the first and second reference lines converge towards oneanother, and wherein the heat exchanger assembly includes a structuralbacking fixed at least partially between the first and secondlongitudinal stiffeners for mounting the heat exchanger assembly.
 4. Thevehicle of claim 1, wherein the heat exchanger assembly is coupled tothe first and second structural members of the structure.
 5. The vehicleof claim 1, wherein the heat exchanger assembly includes a structuralbacking and a cooling tube, wherein the structural backing mounts thecooling tube in position adjacent to, and in thermal communication with,the inside surface of the skin.
 6. The vehicle of claim 5, wherein theheat exchanger assembly further includes an inflatable member operablewith the cooling tube to press the cooling tube towards the insidesurface of the skin, wherein the inflatable member is positioned outsidecooling tube between the cooling tube and the structural backing,wherein the heat exchanger assembly further includes a load applicatorpositioned between inflatable member and the cooling tube, a firststandoff member, and a second standoff member, and wherein the first andsecond standoff members are positioned on opposing sides of the coolingtube and extend from the load applicator towards the inside surface ofthe skin.
 7. The vehicle of claim 1, further comprising: an engine,wherein the thermal management system of the vehicle is thermallycoupled to a heat source of the engine for rejecting heat from the heatsource using the heat exchanger assembly.
 8. The vehicle of claim 1,wherein the first structural member is a first frame member, wherein thesecond structural member is a second frame member, wherein the thermalmanagement system comprises a structural backing and a cooling unit,wherein the cooling unit is formed of an elastic or semi-rigid materialto conform to a shape of the inside surface of the skin.
 9. The vehicleof claim 8, wherein structure further comprises a longitudinal stiffenerextending between the first and second frame members, and wherein thecooling unit extends across the longitudinal stiffener.
 10. A thermalmanagement system for a vehicle, the vehicle comprising a structurehaving a skin defining an inside surface, the thermal management systemcomprising: a heat exchanger assembly comprising a structural backingand a cooling unit, the structural backing configured to mount thecooling unit in a position adjacent to, and in thermal communicationwith, the inside surface of the skin, the cooling unit formed of anelastic or semi-rigid material to conform to a shape of the insidesurface of the skin.
 11. The thermal management system of claim 10,wherein the cooling unit is a cooling tube.
 12. The thermal managementsystem of claim 11, wherein the heat exchanger assembly further includesan inflatable member operable with the cooling tube to press coolingtube towards the inside surface of the skin.
 13. The thermal managementsystem of claim 12, wherein the inflatable member is an inflatablebladder positioned at least partially within the cooling tube.
 14. Thethermal management system of claim 12, wherein the inflatable member ispositioned outside the cooling tube and between the cooling tube and thestructural backing.
 15. The thermal management system of claim 12,wherein the heat exchanger assembly further includes a load applicatorpositioned between the inflatable member and the cooling tube, a firststandoff member, and a second standoff member, and wherein the first andsecond standoff members are positioned on opposing sides of the coolingtube and extend from the load applicator towards the inside surface ofthe skin.
 16. The thermal management system of claim 15, wherein theheat exchanger assembly defines a cooling air passage between the firststandoff member, the cooling tube, and the inner surface of the skin.17. A method of operating a heat exchanger assembly of a thermalmanagement system operable with an inside surface of a skin of a vehiclecomprising: providing a flow of gas to an inflatable member operablewith a cooling unit of the heat exchanger assembly to press cooling unittowards the inside surface of the skin.
 18. The method of claim 17,further comprising: positioning a heat exchanger assembly adjacent to,and in thermal communication with, the inside surface of the skin of thevehicle at a location between a first structural member and a secondstructural member of the structure prior to providing the flow of gas tothe inflatable member.
 19. The method of claim 17, further comprising:determining a condition of the vehicle, of the thermal managementsystem, or both; and modifying a pressure within the inflatable memberin response to the determined condition of the vehicle, of the thermalmanagement system, or both.
 20. The method of claim 19, wherein thecondition is an operating condition of the vehicle, of the thermalmanagement system, or both.